Airflow-dependent deployable fences for aircraft wings

Patent metadata

Field	Value
Publication number	US-11066149-B2
Application number	US-201816197920-A
Country	US
Kind code	B2
Filing date	Nov 21, 2018
Priority date	Nov 21, 2018
Publication date	Jul 20, 2021
Grant date	Jul 20, 2021

Abstract

Airflow-dependent deployable fences for aircraft wings are described. An example apparatus includes a fence coupled to a wing of an aircraft. The fence is movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin. The panel is configured to impede a spanwise airflow along the wing when the fence is in the deployed position. The fence is configured to move from the deployed position to the stowed position in response to an aerodynamic force exerted on the panel.

First claim

What is claimed is:

1. An apparatus comprising:
a fence coupled to a wing of an aircraft, the fence having a leading end oriented toward a leading edge of the wing and a trailing end oriented toward a trailing edge of the wing, the fence being movable relative to the wing between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin, the panel configured to impede a spanwise airflow along the wing when the fence is in the deployed position, the fence configured to move from the deployed position to the stowed position in response to an aerodynamic force exerted on the panel; and
an actuator configured to move the fence from the stowed position to the deployed position in response to the aerodynamic force being less than a threshold force value, the actuator including a forward axle mount coupled to the wing, an aft axle mount coupled to the wing and spaced apart from the forward axle mount, and a spring-loaded axle coupled to and extending between the forward and aft axle mounts, the spring-loaded axle operatively coupled to the fence, the spring-loaded axle including an axle and a spring coiled around the axle, the axle extending through a hole formed in the fence, the spring located between the trailing end of the fence and the aft axle mount.

2. The apparatus of claim 1 , wherein the panel is further configured to generate a vortex along the wing when the fence is in the deployed position.

3. The apparatus of claim 1 , wherein the fence is configured to move from the deployed position to the stowed position during a cruise operation of the aircraft having a first speed, and wherein the fence is further configured to move from the stowed position to the deployed position during a reduced speed operation of the aircraft having a second speed less than the first speed.

4. The apparatus of claim 1 , wherein the spring is configured to wind around the axle in response to the aerodynamic force being greater than the threshold force value, and the spring is further configured to unwind around the axle in response to the aerodynamic force being less than the threshold force value.

5. The apparatus of claim 1 , wherein the axle has a central axis that is canted relative to a chordwise direction of the wing.

6. The apparatus of claim 5 , wherein the central axis is canted at a toe-in angle relative to the chordwise direction of the wing.

7. The apparatus of claim 6 , wherein the panel extends in an inboard direction away from the central axis when the fence is in the stowed position.

8. The apparatus of claim 5 , wherein the central axis is canted at a toe-out angle relative to the chordwise direction of the wing.

9. The apparatus of claim 8 , wherein the panel extends in an outboard direction away from the central axis when the fence is in the stowed position.

10. The apparatus of claim 1 , wherein the panel is recessed within the wing when the fence is in the stowed position.

11. The apparatus of claim 1 , wherein the panel is a first panel of the fence, the first panel having a first orientation relative to a chord of the wing when the fence is in the stowed position, the fence further including a second panel located aft of the first panel, the second panel having a second orientation relative to the chord of the wing when the fence is in the stowed position, the second orientation differing from the first orientation, the first panel and the second panel configured to extend along the skin of the wing when the fence is in the stowed position, the first panel and the second panel configured to impede the spanwise airflow along the wing when the fence is in the deployed position.

12. The apparatus of claim 1 , wherein the panel has a trapezoidal shape between the leading end and the trailing end of the fence.

13. The apparatus of claim 1 , wherein the panel is planar.

14. The apparatus of claim 13 , wherein the panel is parallel to and offset from a central axis of the axle.

15. A method for moving a fence coupled to a wing of an aircraft, the method comprising:
moving the fence between a stowed position in which a panel of the fence extends along a skin of the wing, and a deployed position in which the panel extends at an upward angle away from the skin, the fence having a leading end oriented toward a leading edge of the wing and a trailing end oriented toward a trailing edge of the wing, the panel impeding a spanwise airflow along the wing when the fence is in the deployed position, the moving including:
rotating the fence from the deployed position to the stowed position in response to an aerodynamic force exerted on the panel being greater than a threshold force value; and
rotating the fence from the stowed position to the deployed position via an actuator in response to the aerodynamic force being less than the threshold force value, the actuator including a forward axle mount coupled to the wing, an aft axle mount coupled to the wing and spaced apart from the forward axle mount, and a spring-loaded axle coupled to and extending between the forward and aft axle mounts, the spring-loaded axle operatively coupled to the fence, the spring-loaded axle including an axle and a spring coiled around the axle, the axle extending through a hole formed in the fence, the spring located between the trailing end of the fence and the aft axle mount, the spring biasing the fence toward the deployed position.

16. The method of claim 15 , wherein the panel generates a vortex along the wing when the fence is in the deployed position.

17. The method of claim 15 , wherein the aerodynamic force is generated via a substantially chordwise airflow along a chordwise direction of the wing.

18. The method of claim 17 , wherein a central axis of the axle is canted relative to the chordwise direction of the wing.

19. The method of claim 18 , wherein the central axis is canted at a toe-in angle relative to the chordwise direction of the wing, and wherein the panel extends in an inboard direction away from the central axis when the fence is in the stowed position.

20. The method of claim 18 , wherein the central axis is canted at a toe-out angle relative to the chordwise direction of the wing, and wherein the panel extends in an outboard direction away from the central axis when the fence is in the stowed position.

Assignees

• Boeing Co

Inventors

• Tillotson Brian
• Kettering Chris

Classifications

• B64C3/58 Primary

  provided with fences or spoilers (adjustable for control purposes B64C9/00) · CPC title

• B64C5/12

  for retraction against or within fuselage or nacelle · CPC title

• B64C5/10

  adjustable · CPC title

• B64C5/08 Primary

  mounted on, or supported by, wings · CPC title

• B64C9/00

  Adjustable control surfaces or members, e.g. rudders (trimming stabilising surfaces B64C5/10) · CPC title